CN108087328A - The uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042 and method for designing impeller - Google Patents

Abstract

The invention discloses a kind of uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042 and method for designing impeller, main purpose is the efficiency for improving CO2 compressor group, the power consumption of CO2 compressor group is reduced, ensures that compressor has wider condition range, while the stability of rotor can be improved.The Stage includes：Impeller, vane diffuser, bend and return channel, wherein, the impeller is the entry position for being located at Stage with reference to low frictional resistance wedge shape impeller, the impeller of rule design according to particular vane thickness；The vane diffuser is equipped in the outlet of the impeller, the return channel is located at the outlet port of Stage, is connected between the vane diffuser and the return channel by the bend；The machine Mach number Mu of the Stage₂=0.6~0.9, discharge coefficient Φ₁=0.0042, design point energy head coefficient τ=0.61, polytropic efficiency η under each Mach number_pol=0.62~0.625, the range of flow of application is 71% the 143% of design point.

Description

The uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042 and method for designing impeller

Technical field

The present invention relates to Design of Stage field, more particularly to a kind of uniaxial CO2 compressor end of discharge coefficient 0.0042 Segment model grade and method for designing impeller.

Background technology

The exploitation of modern centrifugal compressor is mostly according to user demand, and based on existing Stage database, utilization is similar Theory carries out conceptual design.Therefore, the quality of Design of Stage directly affects the performance of entire product.It is filled as urea synthesizing The important component put, CO2 compressor group have become major compression because having the characteristics that power pressure is high, density is big Most there are technology content, the most one of product of emphasis in machine producer.

At present, CO2 compressor what discharge coefficient behind high pressure cylinder is all very small, some discharge coefficient Φ₁Even It can be to 0.004 or lower.However, the polytropic efficiency of this small discharge coefficient Stage is generally lower than 60%, it far can not Meets the needs of market.Therefore, it is very great to research and develop the meaning of the small discharge coefficient Stage of efficient CO2 units latter end, is The technical issues of design CO2 compressor field is urgently to be resolved hurrily at present.

The content of the invention

In view of this, the present invention provides a kind of uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042 and impeller is set Meter method, main purpose are the efficiency for improving CO2 compressor group, reduce the power consumption of CO2 compressor sets, ensure compression equipment There is wider condition range, while the stability of rotor can be improved.

According to one aspect of the invention, a kind of uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042 is provided, Including：

The Stage is located in compressor, including impeller (1), vane diffuser (2), bend (3) and return channel (4), Wherein, the impeller (1) is according to low frictional resistance wedge shape impeller of the particular vane thickness distribution with reference to rule design, the impeller (1) it is located at the entry position of Stage；The vane diffuser (2), the return channel are equipped in the outlet of the impeller (1) (4) it is located at the outlet port of Stage, passes through the bend (3) between the vane diffuser (2) and the return channel (4) It is connected；The machine Mach number Mu of the Stage₂=0.6~0.9, discharge coefficient Φ₁=0.0042, design point energy head coefficient τ=0.61, polytropic efficiency η under each Mach number_pol=0.62~0.625, the range of flow of application is the 71%- of design point 143%.

According to another aspect of the invention, a kind of uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042 is provided The design method of middle impeller：

According to default impeller diameter D₂With default hub ratio ds/D₂, calculate hub diameter ds；

According to default impeller blade exit thickness d₂With one-dimensional thermodynamic computing as a result, determining vane inlet established angle β_1A, leaf Take turns exit installation angle β_2A, impeller outlet width b₂, impeller inlet width D₀；

According to the ds, the b₂, the D₀With predefined impeller cover side meridian molded line, the meridional channel of impeller is determined Preliminary moulding；

According to the β_1A, the β_2A, the d₂, default impeller blade import thickness d₁, at the beginning of determining the vane type line of impeller Walk moulding；

According to the preliminary moulding of the meridional channel and the preliminary moulding of the vane type line, impeller is primarily determined that；

Obtained impeller is modeled, and extension processing is carried out to impeller inlet and outlet length；

Three-dimentional structured mesh division is carried out to obtained impeller pattern, ensures that the Yplus values of wall surface first layer grid are small In 1, while the length-width ratio of grid is less than 3000, extends than being less than 3, the minimal orthogonality of grid is more than 15 °；

Three Dimensional Viscous numerical simulation, analysis impeller effect are carried out to the impeller pattern after mesh generation using CFD analysis softwares Rate, condition range, blade flow field；

Whether impeller adiabatic efficiency described in comprehensive descision is more than or equal to default efficiency threshold, and whether the condition range is big In or equal to default condition range threshold value, and whether the blade flow field meets default blade flow field design requirement；

If it is not, the matching of meridional channel and the vane type line is then adjusted, the distribution of modification blade beta angles, vane thickness Distribution, meridian molded line, re-using CFD are analyzed and iterated, until obtaining the impeller adiabatic efficiency more than or equal to default Efficiency threshold, the condition range are more than or equal to default condition range threshold value and the blade flow field meets default impeller The impeller of flow Field Design requirement, the impeller are low frictional resistance wedge shape impeller；

Wherein, the default blade flow field design requirement includes flowing of the impeller on the high section of different leaves without apparent point From；Without flow separation on the meridional channel of impeller；The outlet flow angle of impeller is evenly distributed；Exit static pressure is evenly distributed；Blade Load changes in distribution on pressure face and suction surface is uniform.

The uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042 provided by the invention is single shaft CO2 compressor latter ends Special purpose model grade, efficient, design point energy head coefficient height, hub ratio are big, and vane thickness and height are larger, using the present invention Stage can cause CO2 compressor have higher operational efficiency and wider condition range, reduce CO2 compressor group Power consumption, while the stability of rotor can be improved.In addition, the uniaxial CO2 compressor of discharge coefficient 0.0042 provided by the invention The design method of impeller in latter end Stage can achieve the purpose that reduce wetted perimeter, effectively reduce between fluid and wall surface Friction loss, so as to design low frictional resistance impeller.

Above description is only the general introduction of technical solution of the present invention, in order to better understand the technological means of the present invention, And can be practiced according to the content of specification, and in order to allow above and other objects of the present invention, feature and advantage can It is clearer and more comprehensible, below the special specific embodiment for lifting the present invention.

Description of the drawings

By reading the detailed description of hereafter preferred embodiment, it is various other the advantages of and benefit it is general for this field Logical technical staff will be apparent understanding.Attached drawing is only used for showing the purpose of preferred embodiment, and is not considered as to this hair Bright limitation.And throughout the drawings, the same reference numbers will be used to refer to the same parts.In the accompanying drawings：

Fig. 1 is the schematic diagram for the CO2 compressor Stage that discharge coefficient provided in an embodiment of the present invention is 0.0042；

Fig. 2 is the CO2 compressor Stage impeller disengaging bicker that discharge coefficient provided in an embodiment of the present invention is 0.0042 Schematic diagram；

Fig. 3 be discharge coefficient provided in an embodiment of the present invention be 0.0042 CO2 compressor Stage vane diffuser into Angle of outlet schematic diagram；

Fig. 4 is the CO2 compressor Stage return channel inlet and outlet that discharge coefficient provided in an embodiment of the present invention is 0.0042 Angle schematic diagram；

Fig. 5 flows to impeller blade load distribution schematic diagram for edge provided in an embodiment of the present invention；

Fig. 6 is the high section relative velocity distribution map of 10% leaf of impeller provided in an embodiment of the present invention；

Fig. 7 is the high section relative velocity distribution map of 50% leaf of impeller provided in an embodiment of the present invention；

Fig. 8 is the high section relative velocity distribution map of 90% leaf of impeller provided in an embodiment of the present invention；

Fig. 9 is meridional channel relative velocity distribution map provided in an embodiment of the present invention；

Figure 10 is the impeller outlet air-flow angular distribution provided in an embodiment of the present invention extended to relative position；

Figure 11 is the impeller outlet static pressure distribution figure provided in an embodiment of the present invention extended to relative position；

Figure 12 flows to distribution schematic diagram for wedge-shaped impeller blade angle provided in an embodiment of the present invention with vane thickness edge；

Figure 13 illustrates for wedge-shaped impeller channel profile provided in an embodiment of the present invention with conventional impellers runner silhouette contrast Figure；

Figure 14 is that provided in an embodiment of the present invention extend to the impeller outlet flow angle of relative position is distributed basis for estimation Figure；

Figure 15 is the impeller outlet static pressure distribution basis for estimation figure provided in an embodiment of the present invention extended to relative position；

Figure 16 be edge provided in an embodiment of the present invention flow to impeller blade suction surface and pressure face load distribution judge according to According to figure；

Figure 17 is the high section relative velocity distribution map of 10% leaf of vane diffuser provided in an embodiment of the present invention；

Figure 18 is the high section relative velocity distribution map of 50% leaf of vane diffuser provided in an embodiment of the present invention；

Figure 19 is the high section relative velocity distribution map of 90% leaf of vane diffuser provided in an embodiment of the present invention；

Figure 20 is the high section relative velocity distribution map of 10% leaf of return channel provided in an embodiment of the present invention；

Figure 21 is the high section relative velocity distribution map of 50% leaf of return channel provided in an embodiment of the present invention；

Figure 22 is the high section relative velocity distribution map of 90% leaf of return channel provided in an embodiment of the present invention；

Figure 23 is pressure ratio performance curve schematic diagram under different Mach number provided in an embodiment of the present invention；

Figure 24 is polytropic efficiency performance curve schematic diagram under different Mach number provided in an embodiment of the present invention；

Figure 25 is can head coefficient performance curve schematic diagram under different Mach number provided in an embodiment of the present invention.

Specific embodiment

The exemplary embodiment of the disclosure is more fully described below with reference to accompanying drawings.Although this public affairs is shown in attached drawing The exemplary embodiment opened, it being understood, however, that may be realized in various forms the disclosure without the implementation that should be illustrated here Example is limited.On the contrary, these embodiments are provided to facilitate a more thoroughly understanding of the present invention, and can be by the disclosure Scope is completely communicated to those skilled in the art.

To solve the above-mentioned problems, an embodiment of the present invention provides a kind of uniaxial CO2 compressor ends of discharge coefficient 0.0042 Segment model grade, suitable for the Modulated Design of uniaxial CO2 compressor product, as shown in Fig. 1, the Stage is located in compressor, Including impeller 1, vane diffuser 2, bend 3 and return channel 4, wherein, the impeller 1 is according to particular vane thickness reference gauge The low frictional resistance wedge shape impeller, the impeller 1 that then design are located at the entry position of Stage；Institute is equipped in the outlet of the impeller 1 Vane diffuser 2 is stated, the return channel 4 is located at the outlet port of Stage, the vane diffuser 2 and the return channel 4 Between be connected by the bend 3；As in Figure 2-4, impeller 1, vane diffuser 2, the leaf of return channel 4 are respectively illustrated Piece passes in and out bicker schematic diagram, the machine Mach number Mu of the Stage₂=0.6~0.9, discharge coefficient Φ₁=0.0042, design Point can head coefficient τ=0.61, polytropic efficiency η under each Mach number_pol=0.62~0.625, the range of flow of application is design point 71%-143%, specific performance curve is as shown in Figure 23~25.

The hub ratio for the CO2 compressor Stage that discharge coefficient in the embodiment of the present invention is 0.0042 is very big, than general Stage hub ratio ds/D₂=0.34 improves about 33%, this can greatly improve the stabilization of the rotor using the Stage Property.

Specifically, the impeller 1 is the two-dimensional impeller of enclosed, and the basic parameter of two-dimensional impeller is as follows：Impeller outlet diameter D₂=450m, number of blade Z₁=11, impeller opposite outlet width b₂/D₂=0.0185, b₂For the impeller outlet of the impeller (1) Width；The two-dimensional impeller is close to wheel cap and wheel disc lateral lobe piece stagger angle β_1AsAnd β_1AhIt is 24 °, the two-dimensional impeller Exit vane angle beta close to wheel cap and wheel disc side_2AsAnd β_2AhBe 22 °, impeller blade import thickness be 4mm, impeller blade Exit thickness is 14mm, and thickness is first increases and then decreases from the inlet to the outlet, maximum gauge 18mm, much larger than general blade Thickness, i.e. vane thickness are to increase to 18mm from the 4mm of entrance, then are reduced to 14mm.

The wheel cap side of the impeller 1 and the meridional channel of reel side are by one section of circular arc and two straight lines tangent with it Section is formed, and the pressure face of the impeller (1) and the blade loading maximum position of suction surface are located at 30% length of blade.Such as Fig. 5 Shown, this load is distributed so that the Stage can effectively reduce runner with very high efficiency and wider condition range Interior friction loss.Under each Mach number design conditions, the flowing of the impeller has following features：

1st, impeller is on 10%, 50%, the 90% high section of leaf, the no any flow separation of flowing among impeller channel, As shown in Figure 6 to 8.

2nd, unsteady three-dimensional viscous flows CFD analysis results show on the meridional channel of the impeller also without any stream Dynamic separation, as shown in Figure 9.

3rd, 1 outlet flow angle of impeller is evenly distributed, and average outlet flow angle is 8~12 °, and fluctuation range is less than 5 degree, such as Shown in Figure 10.

4th, 1 exit static pressure distributing homogeneity of impeller is good, and fluctuation range is within the 2% of outlet average static pressure, such as Figure 11 institutes Show.

5th, the polytropic efficiency of impeller is very high, and the polytropic efficiency at impeller outlet is up to 89.5%.

Specifically, the blade of the vane diffuser 2 uses overall height short blade, it is therefore an objective to while efficiency is improved, also Take into account wider condition range.The vane diffuser 2 is close to wheel cap and wheel disc lateral lobe piece stagger angle β_3AsAnd β_3Ah For 8 °, the vane diffuser 2 is close to the exit vane angle beta of wheel cap and wheel disc side_4AsAnd β_4AhIt it is 19 °, diffusion degree is 5.18, the flow losses in vane diffuser are smaller at this time.

The meridian molded line of the reel side of the vane diffuser 2 is made of one section of straight line, and the meridian molded line of shrouding disc side is It is made of one section of circular arc and other three sections of straight lines；Wherein, the meridian molded line of reel side is perpendicular to axial direction.

The entrance width of the vane diffuser (2) and the ratio b of the impeller outlet width of the impeller (1)₃/b₂= 0.841, the entrance relative position D of the vane diffuser (2)₃/D₂=1.067, the outlet of the vane diffuser (2) is opposite Position D₄/D₂=1.45, D₂For impeller outlet diameter, D₃For the vane diffuser (2) inlet diameter, D₄Expand for the blade The outlet diameter of depressor (2).

Above-mentioned design ensure that 1 exit flow of impeller can smoothly enter vane diffuser 2, and will not be because of runner It expands and generates apparent reflux, be particularly advantageous to the flowing of low flow rate condition；2 exit width of vane diffuser and leaf simultaneously The ratio b of 2 entrance width of piece diffuser₄/b₃≈0.786.The design can be very good the flow field at matching impeller outlet, inhibit leaf The flow separation of piece diffuser shrouding disc side reduces flow losses of the vane diffuser without leaf section.It, should as shown in Figure 17~Figure 19 Almost without flow separation on vane diffuser 2.

Optionally, the inlet and outlet width of the bend 3 compares b₅/b₄=1.282, the b₅Go out mouth width for the bend 3 Degree, the b₄For the exit width of the vane diffuser 2, the unsteady three-dimensional viscous flows CFD analysis knots of the Stage Fruit shows that at each Mach number design point 3 internal flow of bend is good, is not clearly separated, as shown in Figure 9.

Optionally, the blade of the return channel 4 be overall height banana airfoil fan, number of blade Z₂=18, the entrance phase of blade To position D₅/D₂=1.431, entrance established angle is 27 °, blade exit relative position D₆/D₂=0.751, exit installation angle is 105 °, the D₅For the blade inlet diameter of the return channel 4, the D₆For the blade exit diameter of the return channel 4.Reflux The definition of device import and export established angle is as shown in Figure 4；The design can be very good the flow field of matching bend outlet, and cause reflux Device exit flow levels off to axial direction, reduces the adverse effect between grade.Meanwhile return channel blade is in each Mach number design conditions Down without apparent flow separation, as shown in Figure 20~Figure 22.The wheel cap side meridian molded line of the return channel 4 tilts straight for one Line segment, the entrance of the return channel 4 and the wheel cap side circular arc of the bend 3 are tangent；Reel side meridian molded line is vertical straight for one Line segment, entrance and the 3 reel side circular arc of bend are tangent；The outlet section shrouding disc side and reel side of the return channel 4 are by one Section circular arc and the straightway tangent with it composition.

The uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042 provided in an embodiment of the present invention compresses for single shaft CO2 Machine latter end special purpose model grade, efficient, design point energy head coefficient height, hub ratio are big, and vane thickness and height are larger, use The Stage of the present invention can cause CO2 compressor to have higher operational efficiency and wider condition range, while can carry The stability of high rotor.

Further, the embodiment of the present invention also provides a kind of core for the CO2 compressor Stage that discharge coefficient is 0.0042 The design method of center portion part impeller, the described method includes：

201st, according to default impeller diameter D₂With default hub ratio ds/D₂, calculate hub diameter ds.

For example, default impeller diameter D₂It can be 450mm, preset hub ratio ds/D₂Can be 0.453.

202nd, according to default impeller blade exit thickness d₂With one-dimensional thermodynamic computing as a result, determining vane inlet established angle β_1A, impeller outlet established angle β_2A, impeller outlet width b₂, impeller inlet width D₀。

For the embodiment of the present invention, the step 202 can specifically include：Utilize impeller eye absolute velocity c₁, impeller Inlet circumference speed u₁And β_1A=tan^-1c₁/u₁+ i determines vane inlet established angle β_1A；

Utilize impeller outlet radial direction discharge coefficientPeripheral speed coefficientWithDetermine impeller Exit installation angle β_2A；

Utilize impeller eye mass flow G, impeller outlet blockage factor τ₂, impeller outlet specific volume compare k_v2, impeller outlet circle Circular velocity u₂, the D₂, impeller eye fluid density ρ_i, it is describedWith default impeller outlet width calculation formula, impeller is calculated Exit width b₂；

Utilize the ds, the D₂, the τ₂, it is describedThe k_v2, velocity coeffficient k_c, impeller inlet specific volume compare k_v0、 Diameter compares K_DWith default impeller inlet width calculation formula, impeller inlet width D is calculated₀；

Wherein, the τ₂Calculation formula be：

The default impeller outlet width calculation formula is：

The default impeller inlet width calculation formula is：

Can be 14mm.Conventional impellers vane thickness is generally constant 4mm or so, and leaf is greatly improved in the present invention Piece thickness, and give the suitable regularity of distribution.

203rd, according to the ds, the b₂, the D₀With predefined impeller cover side meridian molded line, the meridian of impeller is determined The preliminary moulding of runner.

Wherein, the predefined impeller cover side meridian molded line can be it is customized before step 201, specifically, The impeller cover side meridian molded line can be defined as an angled straight lines.Design can be reduced by being defined as angled straight lines Degree of freedom, facilitate subsequent modification.

204th, according to the β_1A, the β_2A, the d₂, default impeller blade import thickness d₁, determine the blade type of impeller The preliminary moulding of line.

For the embodiment of the present invention, the step 204 can specifically include：According to blade angle along meridian flow direction in more Item formula change profile, vane thickness are along meridian flow direction in multinomial change profile, the β_1A, the β_2A, the d₂With default leaf Impeller blade import thickness d₁, determine the preliminary moulding of vane type line of impeller, wherein, the maximum value position of the blade angle exists At 40% length of blade, the maximum value position of vane thickness is at 80% length of blade.Such as Figure 12, blade type is determined with this The preliminary moulding of line.Figure 13 shows for wedge-shaped impeller channel profile provided in an embodiment of the present invention with conventional impellers runner silhouette contrast It is intended to, it can be seen that the runner of wedge-shaped impeller is due to improving vane thickness and blade height so that flow channel cross-section length-width ratio A/b reduces wetted perimeter, so as to effectively reduce the friction loss of impeller internal flowing closer to 1.

205th, according to the preliminary moulding of the meridional channel and the preliminary moulding of the vane type line, impeller is primarily determined that.

206th, obtained impeller is modeled, and extension processing is carried out to impeller inlet and outlet length.

207th, three-dimentional structured mesh division is carried out to obtained impeller pattern.

In embodiments of the present invention, ensure that the Yplus values of wall surface first layer grid are less than 1, while net by step 207 The length-width ratio of lattice is less than 3000, extends than being less than 3, the minimal orthogonality of grid is more than 15 °.

208th, Three Dimensional Viscous numerical simulation is carried out to the impeller pattern after mesh generation using CFD analysis softwares, analyzes leaf Take turns efficiency, condition range, blade flow field.

It should be noted that it is that the grid that will be generated imports CFD analysis softwares using the process of CFD analysis softwares In, Three Dimensional Viscous numerical simulation is carried out to the impeller；Using Spalart-Allmaras turbulence models, working medium is using preferable empty Gas, inlet boundary condition give total temperature, stagnation pressure, axial admission, and export boundary condition gives mass flow；Then what is given is upper It states Parameter analysis and calculates impeller adiabatic efficiency, condition range, blade flow field.

Since the variable considered in design is more, degree of freedom is larger to be set, it is necessary to carry out auxiliary using Multipurpose Optimal Method Meter.Three-dimensional parameterized fitting is carried out to obtained scheme, including lid side molded line, vane thickness distribution and blade angle point Cloth, give each parameter solution interval and each Mach number under the desired value of polytropic efficiency and pressure ratio, using CFD analysis softwares Three Dimensional Viscous optimization is carried out, to seek obtaining optimal case.

209th, whether impeller adiabatic efficiency described in comprehensive descision is more than or equal to default efficiency threshold, and the condition range is It is no to be more than or equal to default condition range threshold value, and whether the blade flow field meets default blade flow field design requirement.

Wherein, the default efficiency threshold and default condition range threshold value can carry out setting originally according to the design needs Inventive embodiments do not limit.For example, default efficiency threshold can be 80%, 85% etc., default condition range threshold value can be 70%-85%, 80%-85% etc..

210th, if it is not, then adjusting the matching of meridional channel and the vane type line, the distribution of modification blade beta angles, blade Thickness distribution, meridian molded line, re-using CFD are analyzed and iterated, and are more than or equal to until obtaining the impeller adiabatic efficiency Default efficiency threshold, the condition range are more than or equal to default condition range threshold value and the blade flow field meet it is default The impeller of blade flow field design requirement.

It should be noted that if the impeller adiabatic efficiency is less than default efficiency threshold, the condition range is less than default operating mode Range threshold or the blade flow field do not meet default blade flow field design requirement, then perform redesign impeller, until It obtains the impeller adiabatic efficiency and is more than or equal to default efficiency threshold, the condition range more than or equal to default operating mode model It encloses threshold value and the blade flow field meets the impeller of default blade flow field design requirement.

Wherein, the impeller is low frictional resistance wedge shape impeller, and the default blade flow field design requirement includes impeller in difference Flowing on the high section of leaf is without being clearly separated；Without flow separation on the meridional channel of impeller；The outlet flow angle distribution of impeller is equal It is even；Exit static pressure is evenly distributed；Load changes in distribution on blade pressure surface and suction surface is uniform.Specifically, impeller stream is met Design requirement is：I impellers 1 are on 10%, 50%, the 90% high section of leaf, the no any stream of flowing among 1 runner of impeller Dynamic separation, as shown in Figure 6 to 8；Also without any flow separation on the meridional channel of II impellers 1, as shown in Figure 9；III The outlet flow angle of impeller 1 is evenly distributed, and outlet flow angle fluctuation range is less than 5 °, as shown in figure 14；IV exit static pressures are distributed Uniformity is good, and fluctuation range is within the 2% of outlet average static pressure, as shown in figure 15；V blade pressure surfaces and suction surface it is quiet Press changes in distribution uniform, as shown in figure 16.

In embodiments of the present invention, the step 210 is specially：To the impeller adiabatic efficiency and operating mode model of CFD analysis gained Carry out integrated judgment is enclosed, and stream field result is analyzed, and when blade flow field does not meet design requirement, then adjusts impeller Noon and the matching of vane type line, by changing the anti-of the distribution of blade beta angles, vane thickness distribution, meridian molded line and CFD analyses Multiple iteration, it is final so that the impeller adiabatic efficiency of gained is more than or equal to default efficiency threshold, the condition range is more than or Person is equal to default condition range threshold value and the blade flow field meets default blade flow field design requirement；At this point, it completes to set Meter.

The design of impeller in the uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042 provided in an embodiment of the present invention Method can achieve the purpose that reduce wetted perimeter, the friction loss between fluid and wall surface effectively be reduced, so as to design Low frictional resistance impeller.

Based on above-mentioned shown method, correspondingly, the embodiment of the present invention additionally provides a kind of computer readable storage medium, Computer program is stored thereon with, which realizes following steps when being executed by processor：

According to default impeller diameter D₂With default hub ratio ds/D₂, calculate hub diameter ds；

According to default impeller blade exit thickness d₂With one-dimensional thermodynamic computing as a result, determining vane inlet established angle β_1A, leaf Take turns exit installation angle β_2A, impeller outlet width b₂, impeller inlet width D₀；

According to the ds, the b₂, the D₀With predefined impeller cover side meridian molded line, the meridional channel of impeller is determined Preliminary moulding；

According to the β_1A, the β_2A, the d₂, default impeller blade import thickness d₁, at the beginning of determining the vane type line of impeller Walk moulding；

According to the preliminary moulding of the meridional channel and the preliminary moulding of the vane type line, impeller is primarily determined that；

Obtained impeller is modeled, and extension processing is carried out to impeller inlet and outlet length；

Three-dimentional structured mesh division is carried out to obtained impeller pattern, to ensure the Yplus values of wall surface first layer grid More than or equal to 1, while the length-width ratio of grid is more than or equal to 3000, extends than being more than or equal to 3, grid is most Small orthogonality is more than 15 °；

Three Dimensional Viscous numerical simulation, analysis impeller effect are carried out to the impeller pattern after mesh generation using CFD analysis softwares Rate, condition range, blade flow field；

Whether impeller adiabatic efficiency described in comprehensive descision is more than or equal to default efficiency threshold, and whether the condition range is big In or equal to default condition range threshold value, and whether the blade flow field meets default blade flow field design requirement；

If it is not, the matching of meridional channel and the vane type line is then adjusted, the distribution of modification blade beta angles, vane thickness Distribution, meridian molded line, re-using CFD are analyzed and iterated, until obtaining the impeller adiabatic efficiency more than or equal to default Efficiency threshold, the condition range are more than or equal to default condition range threshold value and the blade flow field meets default impeller The impeller of flow Field Design requirement, the impeller are low frictional resistance wedge shape impeller；

Wherein, the default blade flow field design requirement includes flowing of the impeller on the high section of different leaves without apparent point From；Without flow separation on the meridional channel of impeller；The outlet flow angle of impeller is evenly distributed；Exit static pressure is evenly distributed；Blade Load changes in distribution on pressure face and suction surface is uniform.

Based on above-mentioned shown method, the discharge coefficient 0.0042 that the embodiment of the present invention is additionally provided described in a kind of design is single Impeller unit in axis CO2 compressor latter end Stage on a memory and can located including memory, processor and storage The computer program run on reason device, the processor realize following steps when performing described program：

According to default impeller diameter D₂With default hub ratio ds/D₂, calculate hub diameter ds；

According to default impeller blade exit thickness d₂With one-dimensional thermodynamic computing as a result, determining vane inlet established angle β_1A, leaf Take turns exit installation angle β_2A, impeller outlet width b₂, impeller inlet width D₀；

According to the ds, the b₂, the D₀With predefined impeller cover side meridian molded line, the meridional channel of impeller is determined Preliminary moulding；

According to the β_1A, the β_2A, the d₂, default impeller blade import thickness d₁, at the beginning of determining the vane type line of impeller Walk moulding；

According to the preliminary moulding of the meridional channel and the preliminary moulding of the vane type line, impeller is primarily determined that；

Obtained impeller is modeled, and extension processing is carried out to impeller inlet and outlet length；

Three-dimentional structured mesh division is carried out to obtained impeller pattern, to ensure the Yplus values of wall surface first layer grid More than or equal to 1, while the length-width ratio of grid is more than or equal to 3000, extends than being more than or equal to 3, grid is most Small orthogonality is more than 15 °；

Three Dimensional Viscous numerical simulation, analysis impeller effect are carried out to the impeller pattern after mesh generation using CFD analysis softwares Rate, condition range, blade flow field；

Whether impeller adiabatic efficiency described in comprehensive descision is more than or equal to default efficiency threshold, and whether the condition range is big In or equal to default condition range threshold value, and whether the blade flow field meets default blade flow field design requirement；

If it is not, the matching of meridional channel and the vane type line is then adjusted, the distribution of modification blade beta angles, vane thickness Distribution, meridian molded line, re-using CFD are analyzed and iterated, until obtaining the impeller adiabatic efficiency more than or equal to default Efficiency threshold, the condition range are more than or equal to default condition range threshold value and the blade flow field meets default impeller The impeller of flow Field Design requirement, the impeller are low frictional resistance wedge shape impeller；

Wherein, the default blade flow field design requirement includes flowing of the impeller on the high section of different leaves without apparent point From；Without flow separation on the meridional channel of impeller；The outlet flow angle of impeller is evenly distributed；Exit static pressure is evenly distributed；Blade Load changes in distribution on pressure face and suction surface is uniform.

The embodiment of the present invention also provides following technical solution：

The uniaxial CO2 compressor latter end Stage of A1, a kind of discharge coefficient 0.0042, including：The Stage is located at compression In machine, including impeller (1), vane diffuser (2), bend (3) and return channel (4), wherein, the impeller (1) is according to specific Vane thickness is located at the entry position of Stage with reference to low frictional resistance wedge shape impeller, the impeller (1) of rule design；Described The outlet of impeller (1) is equipped with the vane diffuser (2), and the return channel (4) is located at the outlet port of Stage, the leaf It is connected between piece diffuser (2) and the return channel (4) by the bend (3)；The machine Mach number of the Stage Mu₂=0.6~0.9, discharge coefficient Φ₁=0.0042, design point energy head coefficient τ=0.61, polytropic efficiency η under each Mach number_pol =0.62~0.625, the range of flow of application is the 71%-143% of design point.

A2, the uniaxial CO2 compressor latter end Stage of the discharge coefficient 0.0042 as described in A1, the latter end Stage Hub ratio ds/D₂=0.453, ds are hub diameter, D₂For the impeller outlet diameter of the impeller (1).

A3, the uniaxial CO2 compressor latter end Stage of the discharge coefficient 0.0042 as described in A1, the impeller (1) is enclosed Two-dimensional impeller, the basic parameter of two-dimensional impeller is as follows：

Impeller outlet diameter D₂=450mm, number of blade Z₁=11, impeller opposite outlet width b₂/D₂=0.0185, for institute State the impeller outlet width of impeller (1)；The two-dimensional impeller is close to wheel cap and wheel disc lateral lobe piece stagger angle β_1AsAnd β_1Ah For 24 °, the two-dimensional impeller is close to the exit vane angle beta of wheel cap and wheel disc side_2AsAnd β_2AhIt it is 22 °, impeller blade import is thick It spends for 4mm, impeller blade exit thickness is 14mm.

The uniaxial CO2 compressor latter end Stage of A4, such as A1 or A3 any one of them discharge coefficient 0.0042,

The wheel cap side of the impeller (1) and the meridional channel of reel side are straight by one section of circular arc and tangent with it two Line segment is formed, and the pressure face of the impeller (1) and the blade loading maximum position of suction surface are located at 30% length of blade.

A5, the uniaxial CO2 compressor latter end Stage of the discharge coefficient 0.0042 as described in A1,

Vane diffuser (2) blade uses overall height short blade, and the vane diffuser (2) is close to wheel cap and wheel disc Lateral lobe piece stagger angle β_3AsAnd β_3AhIt it is 8 °, the vane diffuser (2) is close to the exit vane angle of wheel cap and wheel disc side β_4AsAnd β_4AhIt it is 19 °, diffusion degree is 5.18.

The uniaxial CO2 compressor latter end Stage of A6, such as A1 or A5 any one of them discharge coefficient 0.0042,

The entrance width of the vane diffuser (2) and the ratio b of the impeller outlet width of the impeller (1)₃/b₂= 0.841, the exit width of the vane diffuser (2) and the ratio b of entrance width₄/b₃≈ 0.786, the vane diffuser (2) Entrance relative position D₃/D₂=1.067, the outlet relative position D of the vane diffuser (2)₄/D₂=1.45, D₂For impeller Outlet diameter, D₃For the vane diffuser (2) inlet diameter, D₄For the outlet diameter of the vane diffuser (2).

The uniaxial CO2 compressor latter end Stage of A7, such as A1 or A5 any one of them discharge coefficient 0.0042,

The meridian molded line of the reel side of the vane diffuser (2) is made of one section of straight line, and the meridian molded line of shrouding disc side It is to be made of one section of circular arc and other three sections of straight lines；Wherein, the meridian molded line of reel side is perpendicular to axial direction.

A8, the uniaxial CO2 compressor latter end Stage of the discharge coefficient 0.0042 as described in A1,

The inlet and outlet width of the bend (3) compares b₅/b₄=1.282, the b₅For the exit width of the bend (3), The b₄For the exit width of the vane diffuser (2).

A9, the uniaxial CO2 compressor latter end Stage of the discharge coefficient 0.0042 as described in A1,

The blade of the return channel (4) be overall height banana airfoil fan, number of blade Z₂=18, the entrance of blade is with respect to position Put D₅/D₂=1.431, entrance established angle is 27 °, blade exit relative position D₆/D₂=0.751, exit installation angle is 105 °, The D₅For the blade inlet diameter of the return channel (4), the D₆For the blade exit diameter of the return channel (4).

A10, the uniaxial CO2 compressor latter end Stage of the discharge coefficient 0.0042 as described in A1,

The wheel cap side meridian molded line of the return channel (4) be an angled straight lines section, the entrance of the return channel (4) with The wheel cap side circular arc of the bend (3) is tangent；Reel side meridian molded line is a vertical straight line section, entrance and the bend (3) Reel side circular arc is tangent；The outlet section shrouding disc side and reel side of the return channel (4) are by one section of circular arc and tangent with it straight Line segment forms.

B11, a kind of design such as uniaxial CO2 compressor latter end model of A1-A10 any one of them discharge coefficient 0.0042 Impeller method in grade,

According to default impeller diameter D₂With default hub ratio ds/D₂, calculate hub diameter ds；

According to default impeller blade exit thickness d₂With one-dimensional thermodynamic computing as a result, determining vane inlet established angle β_1A, leaf Take turns exit installation angle β_2A, impeller outlet width b₂, impeller inlet width D₀；

According to the ds, the b₂, the D₀With predefined impeller cover side meridian molded line, the meridional channel of impeller is determined Preliminary moulding；

According to the β_1A, the β_2A, the d₂, default impeller blade import thickness d₁, at the beginning of determining the vane type line of impeller Walk moulding；

According to the preliminary moulding of the meridional channel and the preliminary moulding of the vane type line, impeller is primarily determined that；

Obtained impeller is modeled, and extension processing is carried out to impeller inlet and outlet length；

Three-dimentional structured mesh division is carried out to obtained impeller pattern, to ensure the Yplus values of wall surface first layer grid More than or equal to 1, while the length-width ratio of grid is more than or equal to 3000, extends than being more than or equal to 3, grid is most Small orthogonality is more than 15 °；

Three Dimensional Viscous numerical simulation, analysis impeller effect are carried out to the impeller pattern after mesh generation using CFD analysis softwares Rate, condition range, blade flow field；

Whether impeller adiabatic efficiency described in comprehensive descision is more than or equal to default efficiency threshold, and whether the condition range is big In or equal to default condition range threshold value, and whether the blade flow field meets default blade flow field design requirement；

If it is not, the matching of meridional channel and the vane type line is then adjusted, the distribution of modification blade beta angles, vane thickness Distribution, meridian molded line, re-using CFD are analyzed and iterated, until obtaining the impeller adiabatic efficiency more than or equal to default Efficiency threshold, the condition range are more than or equal to default condition range threshold value and the blade flow field meets default impeller The impeller of flow Field Design requirement, the impeller are low frictional resistance wedge shape impeller；

Wherein, the default blade flow field design requirement includes flowing of the impeller on the high section of different leaves without apparent point From；Without flow separation on the meridional channel of impeller；The outlet flow angle of impeller is evenly distributed；Exit static pressure is evenly distributed；Blade Load changes in distribution on pressure face and suction surface is uniform.

Impeller method in B12, the uniaxial CO2 compressor latter end Stage of the discharge coefficient 0.0042 as described in B11, institute It states according to default impeller blade exit thickness d₂With one-dimensional thermodynamic computing as a result, determining vane inlet established angle β_1A, impeller outlet Established angle β_2A, impeller outlet width b₂, impeller inlet width D₀, specifically include：

Utilize impeller eye absolute velocity c₁, impeller eye peripheral speed u₁And β_1A=tan^-1c₁/u₁+ i, determine blade into Mouth established angle β_1A；

Utilize impeller outlet radial direction discharge coefficientPeripheral speed coefficientWithDetermine impeller Exit installation angle β_2A；

Utilize impeller eye mass flow G, impeller outlet blockage factor τ₂, impeller outlet specific volume compare k_v2, impeller outlet circle Circular velocity u₂, the D₂, impeller eye fluid density ρ_i, it is describedWith default impeller outlet width calculation formula, impeller is calculated Exit width b₂；

Utilize the ds, the D₂, the τ₂, it is describedThe k_v2, velocity coeffficient k_c, impeller inlet specific volume compare k_v0、 Diameter compares K_DWith default impeller inlet width calculation formula, impeller inlet width D is calculated₀；

Wherein, the τ₂Calculation formula be：

The default impeller outlet width calculation formula is：

The default impeller inlet width calculation formula is：

Impeller method in B13, the uniaxial CO2 compressor latter end Stage of the discharge coefficient 0.0042 as described in B11, it is described According to the β_1A, the β_2A, the d₂, default impeller blade import thickness d₁, determine the preliminary moulding of vane type line of impeller, It specifically includes：

Become according to blade angle along meridian flow direction in multinomial change profile, vane thickness along meridian flow direction in multinomial Change distribution, the β_1A, the β_2A, the d₂With default impeller blade import thickness d₁, determine that the vane type line of impeller is tentatively made Type, wherein, the maximum value position of the blade angle is at 40% length of blade, the maximum value position of vane thickness is 80% At length of blade.

Leaf in the uniaxial CO2 compressor latter end Stage of B14, such as B11-B13 any one of them discharge coefficient 0.0042 Wheel method, the predefined impeller cover side meridian molded line are an angled straight lines.

C15, a kind of computer readable storage medium, are stored thereon with computer program, when which is executed by processor Realize following steps：

According to default impeller diameter D₂With default hub ratio ds/D₂, calculate hub diameter ds；

According to default impeller blade exit thickness d₂With one-dimensional thermodynamic computing as a result, determining vane inlet established angle β_1A, leaf Take turns exit installation angle β_2A, impeller outlet width b₂, impeller inlet width D₀；

According to the ds, the b₂, the D₀With predefined impeller cover side meridian molded line, the meridional channel of impeller is determined Preliminary moulding；

According to the β_1A, the β_2A, the d₂, default impeller blade import thickness d₁, at the beginning of determining the vane type line of impeller Walk moulding；

According to the preliminary moulding of the meridional channel and the preliminary moulding of the vane type line, impeller is primarily determined that；

Obtained impeller is modeled, and extension processing is carried out to impeller inlet and outlet length；

Three-dimentional structured mesh division is carried out to obtained impeller pattern, to ensure the Yplus values of wall surface first layer grid More than or equal to 1, while the length-width ratio of grid is more than or equal to 3000, extends than being more than or equal to 3, grid is most Small orthogonality is more than 15 °；

Three Dimensional Viscous numerical simulation, analysis impeller effect are carried out to the impeller pattern after mesh generation using CFD analysis softwares Rate, condition range, blade flow field；

Whether impeller adiabatic efficiency described in comprehensive descision is more than or equal to default efficiency threshold, and whether the condition range is big In or equal to default condition range threshold value, and whether the blade flow field meets default blade flow field design requirement；

If it is not, the matching of meridional channel and the vane type line is then adjusted, the distribution of modification blade beta angles, vane thickness Distribution, meridian molded line, re-using CFD are analyzed and iterated, until obtaining the impeller adiabatic efficiency more than or equal to default Efficiency threshold, the condition range are more than or equal to default condition range threshold value and the blade flow field meets default impeller The impeller of flow Field Design requirement, the impeller are low frictional resistance wedge shape impeller；

Wherein, the default blade flow field design requirement includes flowing of the impeller on the high section of different leaves without apparent point From；Without flow separation on the meridional channel of impeller；The outlet flow angle of impeller is evenly distributed；Exit static pressure is evenly distributed；Blade Load changes in distribution on pressure face and suction surface is uniform.

D16, a kind of design such as uniaxial CO2 compressor latter end model of A1-A10 any one of them discharge coefficient 0.0042 Impeller unit in grade including memory, processor and stores the computer journey that can be run on a memory and on a processor Sequence, the processor realize following steps when performing described program：

According to default impeller diameter D₂With default hub ratio ds/D₂, calculate hub diameter ds；

According to default impeller blade exit thickness d₂With one-dimensional thermodynamic computing as a result, determining vane inlet established angle β_1A, leaf Take turns exit installation angle β_2A, impeller outlet width b₂, impeller inlet width D₀；

According to the ds, the b₂, the D₀With predefined impeller cover side meridian molded line, the meridional channel of impeller is determined Preliminary moulding；

According to the β_1A, the β_2A, the d₂, default impeller blade import thickness d₁, at the beginning of determining the vane type line of impeller Walk moulding；

According to the preliminary moulding of the meridional channel and the preliminary moulding of the vane type line, impeller is primarily determined that；

Obtained impeller is modeled, and extension processing is carried out to impeller inlet and outlet length；

Three-dimentional structured mesh division is carried out to obtained impeller pattern, to ensure the Yplus values of wall surface first layer grid More than or equal to 1, while the length-width ratio of grid is more than or equal to 3000, extends than being more than or equal to 3, grid is most Small orthogonality is more than 15 °；

Three Dimensional Viscous numerical simulation, analysis impeller effect are carried out to the impeller pattern after mesh generation using CFD analysis softwares Rate, condition range, blade flow field；

Whether impeller adiabatic efficiency described in comprehensive descision is more than or equal to default efficiency threshold, and whether the condition range is big In or equal to default condition range threshold value, and whether the blade flow field meets default blade flow field design requirement；

If it is not, the matching of meridional channel and the vane type line is then adjusted, the distribution of modification blade beta angles, vane thickness Distribution, meridian molded line, re-using CFD are analyzed and iterated, until obtaining the impeller adiabatic efficiency more than or equal to default Efficiency threshold, the condition range are more than or equal to default condition range threshold value and the blade flow field meets default impeller The impeller of flow Field Design requirement, the impeller are low frictional resistance wedge shape impeller；

Wherein, the default blade flow field design requirement includes flowing of the impeller on the high section of different leaves without apparent point From；Without flow separation on the meridional channel of impeller；The outlet flow angle of impeller is evenly distributed；Exit static pressure is evenly distributed；Blade Load changes in distribution on pressure face and suction surface is uniform.

In the above-described embodiments, all emphasize particularly on different fields to the description of each embodiment, there is no the portion being described in detail in some embodiment Point, it may refer to the associated description of other embodiment.

It is understood that the correlated characteristic in the above method and device can be referred to mutually.In addition, above-described embodiment In " first ", " second " etc. be for distinguishing each embodiment, and do not represent the quality of each embodiment.

It is apparent to those skilled in the art that for convenience and simplicity of description, foregoing description is The specific work process of system, device and unit, may be referred to the corresponding process in preceding method embodiment, details are not described herein.

Algorithm and display be not inherently related to any certain computer, virtual system or miscellaneous equipment provided herein. Various general-purpose systems can also be used together with example based on this.As described above, required by constructing this kind of system Structure be obvious.In addition, the present invention is not also directed to any certain programmed language.It should be understood that it can utilize various Programming language realizes the content of invention described herein, and the description done above to language-specific is to disclose this The preferred forms of invention.

In the specification provided in this place, numerous specific details are set forth.It is to be appreciated, however, that the implementation of the present invention Example can be put into practice without these specific details.In some instances, well known method, knot is not been shown in detail Structure and technology, so as not to obscure the understanding of this description.

Similarly, it should be understood that in order to simplify the disclosure and help to understand one or more of each inventive aspect, Above in the description of exemplary embodiment of the present invention, each feature of the invention is grouped together into single reality sometimes It applies in example, figure or descriptions thereof.However, the method for the disclosure should be construed to reflect following intention：Want Ask protection the present invention claims the more features of feature than being expressly recited in each claim.More precisely, such as As following claims reflect, inventive aspect is all features less than single embodiment disclosed above. Therefore, it then follows thus claims of specific embodiment are expressly incorporated in the specific embodiment, wherein each right will Ask itself all as separate embodiments of the invention.

Those skilled in the art, which are appreciated that, to carry out adaptivity to the module in the equipment in embodiment Ground changes and they is arranged in one or more equipment different from the embodiment.It can be the module in embodiment Or unit or component are combined into a module or unit or component and can be divided into multiple submodule or son in addition Unit or sub-component.It, can be in addition at least some in such feature and/or process or unit exclude each other Using any combinations to all features disclosed in this specification (including adjoint claim, summary and attached drawing) and such as Any method of the displosure or all processes or unit of equipment are combined.Unless expressly stated otherwise, this specification Each feature disclosed in (including adjoint claim, summary and attached drawing) can be by providing identical, equivalent or similar purpose Alternative features replace.

In addition, it will be appreciated by those of skill in the art that although some embodiments described herein include other embodiments In included some features rather than other feature, but the combination of the feature of different embodiments means in the present invention Within the scope of and form different embodiments.For example, in the following claims, embodiment claimed One of arbitrary mode can use in any combination.

The all parts embodiment of the present invention can be with hardware realization or to be transported on one or more processor Capable software module is realized or realized with combination thereof.It it will be understood by those of skill in the art that can be in practice Centrifugal compressor design dress according to embodiments of the present invention is realized using microprocessor or digital signal processor (DSP) The some or all functions of some or all components in putting.The present invention is also implemented as being retouched here for performing The some or all equipment or program of device (for example, computer program and computer program product) for the method stated. Such program for realizing the present invention can may be stored on the computer-readable medium or can have one or more letter Number form.Such signal can be downloaded from internet website to be obtained either providing or to appoint on carrier signal What other forms provides.

It should be noted that the present invention will be described rather than limits the invention for above-described embodiment, and this Field technology personnel can design alternative embodiment without departing from the scope of the appended claims.In claim In, any reference symbol between bracket should not be configured to limitations on claims.Word "comprising" is not excluded for depositing In element or step not listed in the claims.Word "a" or "an" before element does not exclude the presence of multiple Such element.The present invention can be by means of including the hardware of several different elements and by means of properly programmed calculating Machine is realized.If in the unit claim for listing equipment for drying, several in these devices can be by same A hardware branch embodies.The use of word first, second, and third does not indicate that any order, can be by these words It is construed to title.

Claims (10)

1. a kind of uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042, which is characterized in that including：The model level In in compressor, including impeller (1), vane diffuser (2), bend (3) and return channel (4), wherein, the impeller (1) is root It is located at the entry position of Stage with reference to low frictional resistance wedge shape impeller, the impeller (1) of rule design according to particular vane thickness； The outlet of the impeller (1) is equipped with the vane diffuser (2), and the return channel (4) is located at the outlet port of Stage, described It is connected between vane diffuser (2) and the return channel (4) by the bend (3)；The machine Mach number of the Stage Mu₂=0.6~0.9, discharge coefficient Φ₁=0.0042, design point energy head coefficient τ=0.61, polytropic efficiency η under each Mach number_pol =0.62~0.625, the range of flow of application is the 71%-143% of design point.

2. the uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042 according to claim 1, which is characterized in that

The hub ratio ds/D of the latter end Stage₂=0.453, ds are hub diameter, D₂For the impeller of the impeller (1) Outlet diameter.

3. the uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042 according to claim 1, which is characterized in that institute The two-dimensional impeller that impeller (1) is enclosed is stated, the basic parameter of two-dimensional impeller is as follows：

Impeller outlet diameter D₂=450mm, number of blade Z₁=11, impeller opposite outlet width b₂/D₂=0.0185, it is the impeller (1) impeller outlet width；The two-dimensional impeller is close to wheel cap and wheel disc lateral lobe piece stagger angle β_1AsAnd β_1AhIt is 24 °, The two-dimensional impeller is close to the exit vane angle beta of wheel cap and wheel disc side_2AsAnd β_2AhIt it is 22 °, impeller blade import thickness is 4mm, impeller blade exit thickness are 14mm.

It is 4. special according to the uniaxial CO2 compressor latter end Stage of 1 or 3 any one of them discharge coefficient of claim 0.0042 Sign is,

The wheel cap side of the impeller (1) and the meridional channel of reel side are by one section of circular arc and the two straightway structures tangent with it Into the pressure face of the impeller (1) and the blade loading maximum position of suction surface are located at 30% length of blade.

5. in a kind of 0.0042 uniaxial CO2 compressor latter end Stage of design claim 1-4 any one of them discharge coefficient Impeller method, which is characterized in that

According to default impeller diameter D₂With default hub ratio ds/D₂, calculate hub diameter ds；

According to default impeller blade exit thickness d₂With one-dimensional thermodynamic computing as a result, determining vane inlet established angle β_1A, impeller goes out Mouth established angle β_2A, impeller outlet width b₂, impeller inlet width D₀；

According to the ds, the b₂, the D₀With predefined impeller cover side meridian molded line, determine that the meridional channel of impeller is preliminary Moulding；

According to the β_1A, the β_2A, the d₂, default impeller blade import thickness d₁, determine that the vane type line of impeller is tentatively made Type；

According to the preliminary moulding of the meridional channel and the preliminary moulding of the vane type line, impeller is primarily determined that；

Obtained impeller is modeled, and extension processing is carried out to impeller inlet and outlet length；

Three-dimentional structured mesh division is carried out to obtained impeller pattern, is more than with the Yplus values for ensureing wall surface first layer grid Or equal to 1, while the length-width ratio of grid is more than or equal to 3000, extends than being more than or equal to 3, the minimal orthogonality of grid Property be more than 15 °；

Three Dimensional Viscous numerical simulation, analysis impeller adiabatic efficiency, work are carried out to the impeller pattern after mesh generation using CFD analysis softwares Condition scope, blade flow field；

Whether impeller adiabatic efficiency described in comprehensive descision is more than or equal to default efficiency threshold, the condition range whether be more than or Equal to default condition range threshold value, and whether the blade flow field meets default blade flow field design requirement；

If it is not, then adjusting the matching of meridional channel and the vane type line, modification blade beta angles are distributed, vane thickness is distributed, Meridian molded line, re-using CFD are analyzed and iterated, and are more than or equal to default efficiency threshold until obtaining the impeller adiabatic efficiency Value, the condition range are more than or equal to default condition range threshold value and the blade flow field meets default blade flow field and sets The impeller of requirement is counted, the impeller is low frictional resistance wedge shape impeller；

Wherein, the default blade flow field design requirement includes flowing of the impeller on the high section of different leaves without being clearly separated；Leaf Without flow separation on the meridional channel of wheel；The outlet flow angle of impeller is evenly distributed；Exit static pressure is evenly distributed；Blade pressure surface It is uniform with the load changes in distribution on suction surface.

6. the impeller method in the uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042 according to claim 5, It is characterized in that, the foundation presets impeller blade exit thickness d₂With one-dimensional thermodynamic computing as a result, determining vane inlet established angle β_1A, impeller outlet established angle β_2A, impeller outlet width b₂, impeller inlet width D₀, specifically include：

Utilize impeller eye absolute velocity c₁, impeller eye peripheral speed u₁And β_1A=tan^-1c₁/u₁+ i determines that vane inlet is pacified Fill angle beta_1A；

Utilize impeller outlet radial direction discharge coefficientPeripheral speed coefficientWithDetermine that impeller outlet is pacified Fill angle beta_2A；

Utilize impeller eye mass flow G, impeller outlet blockage factor τ₂, impeller outlet specific volume compare k_v2, impeller outlet circumference speed Spend u₂, the D₂, impeller eye fluid density ρ_i, it is describedWith default impeller outlet width calculation formula, impeller outlet is calculated Width b₂；

Utilize the ds, the D₂, the τ₂, it is describedThe k_v2, velocity coeffficient k_c, impeller inlet specific volume compare k_v0, diameter ratio K_DWith default impeller inlet width calculation formula, impeller inlet width D is calculated₀；

Wherein, the τ₂Calculation formula be：

The default impeller outlet width calculation formula is：

The default impeller inlet width calculation formula is：

7. the impeller method in the uniaxial CO2 compressor latter end Stage of discharge coefficient 0.0042 according to claim 5, It is characterized in that, it is described according to the β_1A, the β_2A, the d₂, default impeller blade import thickness d₁, determine the blade type of impeller The preliminary moulding of line, specifically includes：

It is flowed to according to blade angle along meridian flow direction in multinomial change profile, vane thickness along meridian in multinomial variation point Cloth, the β_1A, the β_2A, the d₂With default impeller blade import thickness d₁, determine the preliminary moulding of vane type line of impeller, In, the maximum value position of the blade angle is at 40% length of blade, the maximum value position of vane thickness is long in 80% blade At degree.

8. according to the leaf in the uniaxial CO2 compressor latter end Stage of claim 5-7 any one of them discharge coefficient 0.0042 Wheel method, which is characterized in that the predefined impeller cover side meridian molded line is an angled straight lines.

9. a kind of computer readable storage medium, is stored thereon with computer program, which is characterized in that the program is held by processor Following steps are realized during row：

According to default impeller diameter D₂With default hub ratio ds/D₂, calculate hub diameter ds；

According to default impeller blade exit thickness d₂With one-dimensional thermodynamic computing as a result, determining vane inlet established angle β_1A, impeller goes out Mouth established angle β_2A, impeller outlet width b₂, impeller inlet width D₀；

According to the ds, the b₂, the D₀With predefined impeller cover side meridian molded line, determine that the meridional channel of impeller is preliminary Moulding；

According to the β_1A, the β_2A, the d₂, default impeller blade import thickness d₁, determine that the vane type line of impeller is tentatively made Type；

According to the preliminary moulding of the meridional channel and the preliminary moulding of the vane type line, impeller is primarily determined that；

Obtained impeller is modeled, and extension processing is carried out to impeller inlet and outlet length；

Three-dimentional structured mesh division is carried out to obtained impeller pattern, is more than with the Yplus values for ensureing wall surface first layer grid Or equal to 1, while the length-width ratio of grid is more than or equal to 3000, extends than being more than or equal to 3, the minimal orthogonality of grid Property be more than 15 °；

Three Dimensional Viscous numerical simulation, analysis impeller adiabatic efficiency, work are carried out to the impeller pattern after mesh generation using CFD analysis softwares Condition scope, blade flow field；

Whether impeller adiabatic efficiency described in comprehensive descision is more than or equal to default efficiency threshold, the condition range whether be more than or Equal to default condition range threshold value, and whether the blade flow field meets default blade flow field design requirement；

If it is not, then adjusting the matching of meridional channel and the vane type line, modification blade beta angles are distributed, vane thickness is distributed, Meridian molded line, re-using CFD are analyzed and iterated, and are more than or equal to default efficiency threshold until obtaining the impeller adiabatic efficiency Value, the condition range are more than or equal to default condition range threshold value and the blade flow field meets default blade flow field and sets The impeller of requirement is counted, the impeller is low frictional resistance wedge shape impeller；

Wherein, the default blade flow field design requirement includes flowing of the impeller on the high section of different leaves without being clearly separated；Leaf Without flow separation on the meridional channel of wheel；The outlet flow angle of impeller is evenly distributed；Exit static pressure is evenly distributed；Blade pressure surface It is uniform with the load changes in distribution on suction surface.

10. in a kind of 0.0042 uniaxial CO2 compressor latter end Stage of design claim 1-4 any one of them discharge coefficient Impeller unit, including memory, processor and storage on a memory and the computer program that can run on a processor, It is characterized in that, the processor realizes following steps when performing described program：

According to default impeller diameter D₂With default hub ratio ds/D₂, calculate hub diameter ds；

According to default impeller blade exit thickness d₂With one-dimensional thermodynamic computing as a result, determining vane inlet established angle β_1A, impeller goes out Mouth established angle β_2A, impeller outlet width b₂, impeller inlet width D₀；

According to the ds, the b₂, the D₀With predefined impeller cover side meridian molded line, determine that the meridional channel of impeller is preliminary Moulding；

According to the β_1A, the β_2A, the d₂, default impeller blade import thickness d₁, determine that the vane type line of impeller is tentatively made Type；

According to the preliminary moulding of the meridional channel and the preliminary moulding of the vane type line, impeller is primarily determined that；

Obtained impeller is modeled, and extension processing is carried out to impeller inlet and outlet length；

Three-dimentional structured mesh division is carried out to obtained impeller pattern, is more than with the Yplus values for ensureing wall surface first layer grid Or equal to 1, while the length-width ratio of grid is more than or equal to 3000, extends than being more than or equal to 3, the minimal orthogonality of grid Property be more than 15 °；

Three Dimensional Viscous numerical simulation, analysis impeller adiabatic efficiency, work are carried out to the impeller pattern after mesh generation using CFD analysis softwares Condition scope, blade flow field；

Whether impeller adiabatic efficiency described in comprehensive descision is more than or equal to default efficiency threshold, the condition range whether be more than or Equal to default condition range threshold value, and whether the blade flow field meets default blade flow field design requirement；

If it is not, then adjusting the matching of meridional channel and the vane type line, modification blade beta angles are distributed, vane thickness is distributed, Meridian molded line, re-using CFD are analyzed and iterated, and are more than or equal to default efficiency threshold until obtaining the impeller adiabatic efficiency Value, the condition range are more than or equal to default condition range threshold value and the blade flow field meets default blade flow field and sets The impeller of requirement is counted, the impeller is low frictional resistance wedge shape impeller；

Wherein, the default blade flow field design requirement includes flowing of the impeller on the high section of different leaves without being clearly separated；Leaf Without flow separation on the meridional channel of wheel；The outlet flow angle of impeller is evenly distributed；Exit static pressure is evenly distributed；Blade pressure surface It is uniform with the load changes in distribution on suction surface.